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A Highly Accurate Beam Finite Element for Curved and Twisted Helicopter Blades

[+] Author Affiliations
Yan Skladanek

Eurocopter, Marignane; Université de Lyon, Villeurbanne, France

Paul Cranga

Eurocopter, Marignane, France

Guy Ferraris, Georges Jacquet, Régis Dufour

Université de Lyon, Villeurbanne, France

Paper No. DETC2011-47055, pp. 821-830; 10 pages
doi:10.1115/DETC2011-47055
From:
  • ASME 2011 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference
  • Volume 1: 23rd Biennial Conference on Mechanical Vibration and Noise, Parts A and B
  • Washington, DC, USA, August 28–31, 2011
  • Conference Sponsors: Design Engineering Division and Computers and Information in Engineering Division
  • ISBN: 978-0-7918-5478-5
  • Copyright © 2011 by ASME

abstract

Blade optimization is more than ever a crucial activity for helicopter manufacturers, always looking for performance improvements, noise reduction and vibratory comfort increase. Latest studies have led to design new blade concepts including a double swept plan shape, an evolutionary and increased twist angle at the tip and a new layout for internal components like roving spars. Such blades exhibit a highly coupled behavior between torsion, longitudinal and bending motions that should be accurately modeled for predictive numerical tools. In this research a highly accurate beam finite element is formulated in the rotating frame to improve the static deformation calculation under aerodynamic and centrifugal loads and thus enhance dynamic and stability analysis usually performed for a helicopter development. Numerical and experimental investigations are performed to demonstrate the model reliability both for academic beams with extreme shape and for actual blade design.

Copyright © 2011 by ASME

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